Turbine blade having a constant thickness airfoil skin

摘要

A turbine blade for a gas turbine comprising: a support structure comprising a base defining a root of said blade and a framework extending radially outwardly from said base; a skin coupled to said support structure framework, said framework and said skin defining an airfoil of said blade; and a damping element extending through openings provided in said support structure framework, said damping element comprising a rod having at least one member making contact with and extending between opposing sections of said skin, said member damping vibrations in said skin.